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Laminate composite wing structures

A composite material and wing technology, applied in the field of systems for strengthening wings, can solve problems such as stringers being easily affected by overturning loads

Active Publication Date: 2016-07-27
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Furthermore, the structural features of such curved blade stringers may render these stringers more susceptible to overturning loads

Method used

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  • Laminate composite wing structures
  • Laminate composite wing structures
  • Laminate composite wing structures

Examples

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Effect test

example 1

[0045] This example describes an exemplary aircraft 100; see Figure 1 to Figure 7 .

[0046] Such as figure 1 As shown, aircraft 100 may include a pair of wings 104 (eg, in figure 2 with image 3 in the three-piece wing embodiment configuration shown or in Figure 8 to Figure 11 In the illustrated embodiment configuration of a single-piece wing, which will be described in further detail below), a fuselage 108 , a tail 112 and one or more propulsion units 116 .

[0047] Each of the wings 104 may extend outwardly in the fuselage 108 , for example from an inboard portion 104 a to a respective outboard portion 104 b , in a generally parallel spanwise direction D1 of the wing 104 . Wing 104 (or each wing in wing 104) may include control surfaces 118, lower wing skin 120, upper wing skin 124, front spar 128, rear spar 132, a plurality of stringers 136, and a plurality of A wing rib 140.

[0048] Stringers 136 and lower wing skin 120 (in addition to other components of wing 1...

example 2

[0097] This example describes an exemplary single-piece wing implementation that may alternatively be included in aircraft 100; see Figure 8 to Figure 11 .

[0098] In this example, from Figure 8 and Figure 9 As can be seen in , the wing skin 120 may be continuous (or substantially continuous) between the wingtips 104c, 104d of the wing 104 . Further, stringer 136 may include a plurality of stringers (eg, stringers 800a-i), each of which is similar in structure to stringer 136g described above.

[0099] As can be seen, each of the stringers 800a - i may be curved and extend continuously from one wing 104 to the adjacent wing 104 in the aircraft 100 . For example, stringers 800a-i (eg, such as Figure 8 and Figure 11 shown in the direction toward the tail) has one or more sweeping curvatures and (for example, as Figure 9 and Figure 10 shown, in the upward direction) has one or more dihedral curvatures. The one or more relative axes of general curvature may be subs...

example 3

[0106] This example describes how to stabilize a wing; see Figure 12 . Aspects of components described herein can be used in the method steps described below. Where appropriate, reference is made to components and systems previously described which can be used to perform each step. These references are by way of example and are not intended to limit the possible ways of performing any particular step of the method.

[0107] Figure 12 The flowcharts illustrate steps performed in exemplary methods and may not detail complete processes. Specifically, Figure 12 Depicted are a number of steps of a method (shown generally at 1200 in the figure) that may be performed in conjunction with embodiments disclosed in accordance with aspects of the present disclosure. Although in Figure 12 The various steps of method 1200 may be depicted in and described below, but these steps do not necessarily need to be performed in all, and in some cases may be performed in an order different ...

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PUM

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Abstract

The application discloses laminate composite wing structures. A wing may include a wing skin, a laminate composite first stringer, a rib, and at least one fastener. A majority of the first stringer may be characterized by a stacked plurality of generally planar plies of reinforcement material structurally joined as a stack to an interior surface of the wing skin and extending generally parallel to the interior surface and a span-wise direction of the wing along a substantial portion of the interior surface. The first stringer may have a generally solid trapezoidal cross section when viewed in a plane that is generally perpendicular to the span-wise direction. The rib may be positioned adjacent the interior surface, and may extend generally perpendicular to the span-wise direction. The trapezoidal cross section may be interfaced with the rib flange. The fastener may extend through the wing skin, the trapezoidal cross section, and the rib flange.

Description

technical field [0001] The present disclosure relates to laminated composite wing structures. More specifically, the disclosed embodiments relate to systems and methods for stiffening an airfoil, such as an aircraft wing assembly, an aircraft horizontal tail assembly, and / or a control surface torque box assembly. Background technique [0002] For aircraft structures, it is desirable to be able to handle loads in a variety of different directions. For example, an aircraft wing is expected to be able to cope with the aerodynamic loads imposed on the wing while in flight. Such aerodynamic loads include bending loads reacted by the wing box structure of the wing or components thereof. [0003] Generally, the wing box structure of an aircraft includes a stiffened upper wing panel, a stiffened lower wing panel, a front spar connecting the leading edge of the wing panel, a rear spar connecting the trailing edge of the wing panel, and providing shape and support and connecting to ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/18
CPCB64C3/18B64C3/26B64C1/064B64C3/182B64C3/187B64C1/12B64C3/20Y02T50/40
Inventor 约尔丹·查尔斯威廉·M·桑佩德罗-汤普森杰茜卡·L·沃特金斯瑞安·克里斯托弗·罗彻迈克尔·约翰·甘布尔泰勒·W·唐尼温德尔·C·K·乔伊格雷戈里·M·圣蒂尼
Owner THE BOEING CO
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